EP2831393A1 - Turbojet engine nacelle air intake structure of laminar type - Google Patents

Turbojet engine nacelle air intake structure of laminar type

Info

Publication number
EP2831393A1
EP2831393A1 EP13715366.4A EP13715366A EP2831393A1 EP 2831393 A1 EP2831393 A1 EP 2831393A1 EP 13715366 A EP13715366 A EP 13715366A EP 2831393 A1 EP2831393 A1 EP 2831393A1
Authority
EP
European Patent Office
Prior art keywords
junction
panel
air intake
acoustic
flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13715366.4A
Other languages
German (de)
French (fr)
Inventor
Jean-Philippe Joret
André BAILLARD
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aircelle SA filed Critical Aircelle SA
Publication of EP2831393A1 publication Critical patent/EP2831393A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

  • the present invention relates to an air intake structure for a turbojet engine nacelle.
  • an aircraft propulsion unit conventionally comprises a turbojet engine housed inside a nacelle.
  • the nacelle generally has an annular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of said turbojet engine and its casing, and a downstream section intended to surround the combustion chamber of the turbojet engine and sheltering as the case may be. thrust reverser means.
  • the air intake structure serves to optimize the air intake necessary to supply the fan of the turbojet engine and to channel it towards this fan.
  • An air intake structure comprises in particular upstream a leading edge structure commonly called "lip" air inlet.
  • the air intake lip ensures the capture of air and is attached to the rest of the air intake structure which ensures the channeling of the air captured to the turbojet engine.
  • the remainder of the air intake structure has a substantially annular structure comprising an outer panel providing external aerodynamic continuity of the nacelle and an inner panel ensuring the aerodynamic continuity of the nacelle internally, particularly with the housing of blower at the middle section.
  • the air inlet lip ensures the junction between these two walls and can in particular be integrated into the outer panel.
  • Such nacelles comprising an air intake lip integrated in the outer panel are called “laminar” and the outer panel / air inlet lip assembly can be mounted to move in translation in a longitudinal direction of the nacelle, to allow its upstream opening.
  • laminar Such a nacelle is described in documents FR 2 906 568 and EP 2 344 385, for example.
  • the inner surface of the air intake structure is exposed to a large air flow and is located near the blades of the blower. It is therefore located in a zone of significant noise.
  • the inner panel of the air intake section is equipped with an acoustic attenuation structure.
  • This acoustic attenuation structure is in the form of a honeycomb core sandwich panel having a pierced outer skin, called acoustic skin, intended to be exposed to noise, and a solid inner skin ensuring in particular the mechanical strength of the panel.
  • the alveolar soul thus constitutes a resonator capable of trapping sound waves.
  • the air intake lip may also be equipped with an acoustic attenuation structure on an internal portion thereof.
  • the air intake lip and the inner panel are equipped with connecting flanges, latch means for example, aerodynamic continuity bibs, bumpers, etc.
  • This junction causes a loss of available acoustic surface related to the volume required for the establishment of these joints, bibs and bumpers, among others.
  • the bumpers serve as a centering device between the lip and the inner panel and its attached to the air inlet lip panel by means of screws, with a nut-side access inside a C of closing.
  • the same assembly principle is used for the aerodynamic bib.
  • the lip flange is also used as a support for the installation of a peripheral seal and also serves as a support for the bumpers and the aerodynamic bib. All these functions impact the beginning of the acoustic zone on either side of said junction zone. There is therefore a need for a solution for centering and maintaining such a structure to reduce the non-equipable junction area with an acoustic attenuation structure.
  • the present invention relates to an air inlet structure for a turbojet engine nacelle comprising at least one inner panel intended to be attached to a fan casing of the turbojet and thus to constitute a fixed part of said air intake.
  • air and at least one outer panel movable in translation in a substantially longitudinal direction of the nacelle and incorporating an air inlet lip portion adapted to ensure a junction between the fixed inner panel and the outer panel, said portion of air intake lip and said fixed inner panel being each equipped at least at a junction end with an acoustic attenuation structure, characterized in that at least one of the junction ends is equipped with at least one radial knocker adapted to come into contact with a corresponding junction flange presented by the other end junction when the movable outer panel is positi closing.
  • the hob is integrated with the acoustic panel of its junction end.
  • the knocker may be reported, in particular by gluing.
  • the corresponding flange is integrated with the acoustic panel of its junction end.
  • it may also be reported, especially by gluing.
  • the structure comprises several knockers distributed over a circumference of the junction end.
  • At least one of the contact surfaces of the knocker and the flange is equipped with a coating with a low coefficient of friction. It may especially be a Teflon type coating.
  • Such a coating, Teflon tape or other, provides a low friction coating which can be used as a wear part.
  • the junction of acoustical panels is equipped with at least one aerodynamic flange seal.
  • the junction is equipped with at least one seal.
  • the seal is located between an acoustic panel, and the flange.
  • FIG. 1 is a partial schematic representation in longitudinal section of a so-called “laminar” air intake structure equipped with a centering device according to the prior art
  • FIGS. 2 and 3 are partial diagrammatic representations in longitudinal section of a junction between an inner panel and an air intake lip portion equipped with a centering system according to the invention
  • FIGS. 4a, 4b, 5a, 5b and 6a to 6d are partial schematic representations of the steps of setting up an aerodynamic flange seal
  • FIGS. 7 and 8 are diagrammatic representations in longitudinal section of an alternative embodiment of the invention.
  • FIG. 9 is a schematic cross-sectional representation corresponding to the air intake structure of FIGS. 7 and 8,
  • FIGS. 10a to 10d are partial diagrammatic representations of the installation of the aerofoil flange gasket
  • the present invention more particularly applies to so-called "laminar" nacelles having an air inlet structure 1, an outer wall 2 of which is mounted to move in translation in a longitudinal direction of the nacelle and incorporates a lip portion 2a of air inlet.
  • such an air intake structure for a turbojet engine nacelle comprises at least one inner panel 3 intended to be attached to a fan casing (not visible) of the turbojet engine and thus to constitute a fixed part of said air intake.
  • air 1 and at least one outer panel 2 movable in translation in a substantially longitudinal direction of the nacelle and incorporating an air intake lip portion 2a adapted to provide a junction A0 between the fixed inner panel 3 and the outer panel 2.
  • said air inlet lip portion 2a and said fixed inner panel 3 are each equipped at least at a junction end with an acoustic attenuation structure in the form of a panel 5, 6 honeycomb sandwiches.
  • the centering of the outer wall 2 and the air inlet lip 2a with the inner panel 3 is provided at a junction A0 between said portion of air inlet lip 2a and said inner wall 3 by means of knockers 7 fixed in the lip-side acoustic panel 2a by means of a screw 7a with a nut-side access inside a C closing 7b.
  • An aerodynamic bib 8 to optimize the flow of air flow at the junction between the panels is set according to the same principle.
  • a flange 9 fixed in the inner panel 3 comes, during the closing of the outer panel 2, against a seal 10 carried by a corresponding flange 1 1 of the lip portion 2a of air inlet to ensure the l sealing of the interior of the air intake structure 1.
  • This flange also allows support for the knockers 7 and 8 aerodynamic bib.
  • the acoustic panel 6 of the inner panel 3 has a junction end equipped with a radial knocker 81 on which is able to rest a corresponding junction flange 91 fitted to one end joining the acoustic panel 5 of the air intake lip portion 2a when the latter is in the closed position.
  • the knocker 81 carries a coating strip 82 of Teflon type with a low coefficient of friction.
  • the coating strip 82 with a low coefficient of friction may be carried by the flange 91 junction.
  • This coating strip has a dual function, namely reduction of friction during closing of the air inlet, and wear part.
  • the coating strip may be disposed either on the knocker side 81, or fixed under the flange 91, or be present on both elements.
  • the connecting flange 91 has an end return 91a carrying a seal 10 adapted to cooperate with a flange 92d. corresponding seal carried by the inner panel ( Figure 2).
  • a seal 101 may be mounted at the junction end of the inner panel 3 and come into contact with the connecting flange 91 to ensure sealing closer to said junction A0.
  • the seal 101 may be integrated or attached to the connecting flange 91 in particular to abut against the inner panel 3 during closing.
  • junction flange 91 and the flange 92 of the inner panel 3 can then be used for the introduction of axial stops 20 and / or locks between the lip portion 2a / outer panel 2 and the inner panel 3.
  • the seal 1 0, 1 01 will equip the entire circumference of the structure.
  • the knockers 81 will also advantageously be arranged along the circumference of the structure 1 and preferentially distributed discretely, advantageously uniformly. Of course, it may also be a continuous knocker 81 describing substantially the entire circumference.
  • the beginnings of the acoustic surfaces of the air intake lip portion 2a and of the inner panel 3 are as close as possible to the A0 junction between these two panels, which improves the acoustic treatment of the entire air intake structure 1.
  • junction AO between the air intake lip portion 2a and the inner panel 3 may also be equipped with an aerodynamic flange seal 102.
  • the aerodynamic flap 102 has a flexible elastic structure mounted on an upper skin of an acoustic panel 5 of the lip portion 2a of air inlet.
  • the flap 102 extends along the thickness of said acoustic panel 5 at its junction end A0 and has a lower return 102a extending on either side of said junction A0, both on the lip portion. 2a of air intake only on the inner panel (not shown in Figures 4a, 4b, 5a, 5b), thus providing an aerodynamic recovery of the junction.
  • Figures 4a and 5a are cross-sectional front views of said aerodynamic bib seal 102.
  • a lower part of the flap deviates from the acoustic panel and allows the mounting of the acoustic panel belonging to the inner panel.
  • FIGS 7 to 9 and 10a to 10d are views of a second embodiment of an air intake structure 1 10 according to the invention in which the knockers 81 belong to the acoustic panel 5 of the portion of lip 2a and the connecting flange 91 belongs to the acoustic panel 6 of the inner panel 3.
  • Figure 7 is in longitudinal sectional view taken substantially at locking means 21 (or axial stops 20).
  • Figure 8 is a longitudinal sectional view taken in current section.
  • Figure 9 is a cross sectional view of the face in current section.
  • Figures 10a to 10d are substantially equivalent to Figures 6a to 6d and illustrate the establishment of the seal 102 aerodynamic flap. Note also that in this embodiment, the seal 102 also performs the function of the seal 10 and 101 by means of an upper tab 104 which comes into contact against the connecting flange 91 when closing the structure (closing direction represented by the arrow in Figure 10c).
  • the translatable air inlet generally forms an adjustable removable sleeve on a conduit formed by the base structure of the nacelle.
  • the centering and sealing system object of the present invention can be applied generally to any type of removable sleeve that would be desired to centrally position and sealed on one end of a conduit.

Abstract

The present invention relates to an air intake structure for a turbojet engine nacelle, comprising at least an internal panel (3) intended to be attached to a fan casing, and at least an external panel (2) capable of a translational movement in a substantially longitudinal direction of the nacelle and incorporating a portion of the air inlet lip (2a) able to provide a join between the fixed internal panel and the external panel, said air inlet lip portion and said fixed internal panel each being equipped, at least in the region of a joining end, with an acoustic attenuation structure (5, 6), characterized in that at least one of the joining ends is equipped with at least one radial buffer (81) able to come into contact with a corresponding joining flange (91) exhibited by the other joining end when the mobile external panel is in the closed position

Description

Structure d'entrée d'air de nacelle de turboréacteur de type laminaire  Laminar-type turbojet engine nacelle air intake structure
La présente invention se rapporte à une structure d'entrée d'air pour nacelle de turboréacteur. The present invention relates to an air intake structure for a turbojet engine nacelle.
Comme cela est connu en soit, un ensemble propulsif d'aéronef comprend classiquement un turboréacteur logé à l'intérieur d'une nacelle.  As is known in itself, an aircraft propulsion unit conventionally comprises a turbojet engine housed inside a nacelle.
La nacelle présente généralement une structure annulaire comprenant une entrée d'air en amont du turboréacteur, une section médiane destinée à entourer une soufflante dudit turboréacteur et son carter, et une section aval destinée à entourer la chambre de combustion du turboréacteur et abritant le cas échéant des moyens d'inversion de poussée.  The nacelle generally has an annular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of said turbojet engine and its casing, and a downstream section intended to surround the combustion chamber of the turbojet engine and sheltering as the case may be. thrust reverser means.
Elle peut être terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.  It can be terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
La structure d'entrée d'air sert à optimiser la captation d'air nécessaire à l'alimentation de la soufflante du turboréacteur et à le canaliser vers cette soufflante.  The air intake structure serves to optimize the air intake necessary to supply the fan of the turbojet engine and to channel it towards this fan.
Une structure d'entrée d'air comprend notamment en amont une structure de bord d'attaque couramment appelée « lèvre » d'entrée d'air.  An air intake structure comprises in particular upstream a leading edge structure commonly called "lip" air inlet.
La lèvre d'entrée d'air assure la captation de l'air et est rattachée au reste de la structure d'entrée d'air qui assure la canalisation de l'air capté vers le turboréacteur.  The air intake lip ensures the capture of air and is attached to the rest of the air intake structure which ensures the channeling of the air captured to the turbojet engine.
Pour ce faire, le reste de la structure d'entrée d'air présente une structure sensiblement annulaire comprenant un panneau externe assurant la continuité aérodynamique externe de la nacelle et un panneau interne assurant la continuité aérodynamique interne de la nacelle, notamment avec le carter de soufflante au niveau de la section médiane. La lèvre d'entrée d'air assure la jonction entre ces deux parois et peut notamment être intégrée au panneau externe.  To do this, the remainder of the air intake structure has a substantially annular structure comprising an outer panel providing external aerodynamic continuity of the nacelle and an inner panel ensuring the aerodynamic continuity of the nacelle internally, particularly with the housing of blower at the middle section. The air inlet lip ensures the junction between these two walls and can in particular be integrated into the outer panel.
De telles nacelles comprenant une lèvre d'entrée d'air intégrée au panneau externe sont dites « laminaires » et l'ensemble panneau externe/lèvre d'entrée d'air peut être monté mobile en translation selon une direction longitudinale de la nacelle, de manière à permettre son ouverture amont. Une telle nacelle est décrite dans les documents FR 2 906 568 et EP 2 344 385, par exemple. La surface interne de la structure d'entrée d'air est exposée à un flux d'air important et est située à proximité des pâles de la soufflantes. Elle est donc située dans une zone de bruit important. Such nacelles comprising an air intake lip integrated in the outer panel are called "laminar" and the outer panel / air inlet lip assembly can be mounted to move in translation in a longitudinal direction of the nacelle, to allow its upstream opening. Such a nacelle is described in documents FR 2 906 568 and EP 2 344 385, for example. The inner surface of the air intake structure is exposed to a large air flow and is located near the blades of the blower. It is therefore located in a zone of significant noise.
Afin de remédier au mieux à cette situation et en vue de diminuer la pollution sonore générée par le turboréacteur, le panneau interne de la section d'entrée d'air est équipé d'une structure d'atténuation acoustique.  In order to best remedy this situation and to reduce the noise pollution generated by the turbojet engine, the inner panel of the air intake section is equipped with an acoustic attenuation structure.
Cette structure d'atténuation acoustique se présente sous la forme d'un panneau sandwich à âme alvéolaire possédant une peau externe percée, dite peau acoustique, destinée à être exposée au bruit, et une peau interne pleine assurant notamment al tenue mécanique du panneau. L'âme alvéolaire constitue ainsi un résonateur apte à piéger les ondes sonores.  This acoustic attenuation structure is in the form of a honeycomb core sandwich panel having a pierced outer skin, called acoustic skin, intended to be exposed to noise, and a solid inner skin ensuring in particular the mechanical strength of the panel. The alveolar soul thus constitutes a resonator capable of trapping sound waves.
La lèvre d'entrée d'air peut également être équipée d'une structure d'atténuation acoustique sur une portion interne de celle-ci.  The air intake lip may also be equipped with an acoustic attenuation structure on an internal portion thereof.
Dans le cas d'une nacelle laminaire présentant un capot externe mobile formé par le panneau externe et la lèvre d'entrée d'air, il existe une jonction au niveau de la face interne de la structure d'entrée d'air entre l'extrémité interne de la lèvre d'entrée d'air et l'extrémité amont du panneau externe.  In the case of a laminar nacelle having a movable outer cover formed by the outer panel and the air inlet lip, there is a junction at the inner face of the air inlet structure between the inner end of the air inlet lip and the upstream end of the outer panel.
Afin d'assurer le positionnement, le centrage et le verrouillage de la structure mobile sur le panneau interne fixe en position de fonctionnement, la lèvre d'entrée d'air et le panneau interne sont équipés de brides de jonction, de moyen s d e verrou i l l ag e, jo i nts d 'éta n ché ité , bavette de conti n u ité aérodynamique, butoirs, etc ..  In order to ensure the positioning, centering and locking of the movable structure on the fixed inner panel in the operating position, the air intake lip and the inner panel are equipped with connecting flanges, latch means for example, aerodynamic continuity bibs, bumpers, etc.
Cette jonction entraîne une perte de la surface acoustique disponible liée au volume nécessaire à la mise en place de ces joints, bavettes, et butoirs, entre autres.  This junction causes a loss of available acoustic surface related to the volume required for the establishment of these joints, bibs and bumpers, among others.
Plus précisément, les butoirs servent de dispositif de centrage entre la lèvre et le panneau interne et son fixés sur le panneau côté lèvre d'entrée d'air au moyen de vis, avec un accès côté écrou à l'intérieur d'un C de fermeture. Le même principe d'assemblage est utilisé pour la bavette aérodynamique.  Specifically, the bumpers serve as a centering device between the lip and the inner panel and its attached to the air inlet lip panel by means of screws, with a nut-side access inside a C of closing. The same assembly principle is used for the aerodynamic bib.
La bride côté lèvre est également utilisée comme appui pour la mise en place d'un joint d'étanchéité périphérique et sert également d'appui pour les butoirs et la bavette aérodynamique. Toutes ces fonctions impactent le début de la zone acoustique de part et d'autre de ladite zone de jonction. Il existe donc un besoin pour une solution de centrage et maintien d'une telle structure permettant de réduire la zone de jonction non équipable avec une structure d'atténuation acoustique. The lip flange is also used as a support for the installation of a peripheral seal and also serves as a support for the bumpers and the aerodynamic bib. All these functions impact the beginning of the acoustic zone on either side of said junction zone. There is therefore a need for a solution for centering and maintaining such a structure to reduce the non-equipable junction area with an acoustic attenuation structure.
Pour ce faire, la présente invention se rapporte à une structure d'entrée d'air pour nacelle de turboréacteur comprenant au moins un panneau interne destinée à être rattaché à un carter de soufflante du turboréacteur et à constituer ainsi une partie fixe de ladite entrée d'air, et au moins un panneau externe mobile en translation selon une direction sensiblement longitudinale de la nacelle et intégrant une portion de lèvre d'entrée d'air apte à assurer une jonction entre le panneau interne fixe et le panneau externe, ladite portion de lèvre d'entrée d'air et ledit panneau interne fixe étant chacun équipés au moins au niveau d'une extrémité de jonction, d'une structure d'atténuation acoustique, caractérisé en ce qu'au moins l'une des extrémités de jonction est équipée d'au moins un heurtoir radial apte à venir en contact avec une bride de jonction correspondante présentée par l'autre extrémité de jonction lorsque le panneau externe mobile est en position de fermeture.  To this end, the present invention relates to an air inlet structure for a turbojet engine nacelle comprising at least one inner panel intended to be attached to a fan casing of the turbojet and thus to constitute a fixed part of said air intake. air, and at least one outer panel movable in translation in a substantially longitudinal direction of the nacelle and incorporating an air inlet lip portion adapted to ensure a junction between the fixed inner panel and the outer panel, said portion of air intake lip and said fixed inner panel being each equipped at least at a junction end with an acoustic attenuation structure, characterized in that at least one of the junction ends is equipped with at least one radial knocker adapted to come into contact with a corresponding junction flange presented by the other end junction when the movable outer panel is positi closing.
Ainsi, en prévoyant d'équiper directement les panneaux d'atténuation acoustique d'éléments de centrage (heurtoir/bride), il n'y a plus de perte de surface acoustique due à la fixation de ces éléments.  Thus, by providing to equip directly acoustic attenuation panels of centering elements (knocker / flange), there is more loss of acoustic surface due to the attachment of these elements.
De man ière préférentiel le, heu rtoir est intég ré au panneau acoustique de son extrémité de jonction. Alternativement, le heurtoir pourra être rapporté, notamment par collage.  In a preferred manner, the hob is integrated with the acoustic panel of its junction end. Alternatively, the knocker may be reported, in particular by gluing.
De manière préférentielle, la bride correspondante est intégrée au pan neau acoustiq ue de son extrém ité de jonction . Bien évidemment, alternativement, elle pourra également être rapportée, notamment par collage.  Preferably, the corresponding flange is integrated with the acoustic panel of its junction end. Of course, alternatively, it may also be reported, especially by gluing.
De manière avantageuse, la structure comprend plusieurs heurtoirs répartis sur une circonférence de l'extrémité de jonction.  Advantageously, the structure comprises several knockers distributed over a circumference of the junction end.
Avantageusement, au moins u ne des surfaces de contact du heurtoir et de la bride est équipée d'un revêtement à faible coefficient de frottement. Il pourra notamment s'agir d'un revêtement de type téflon.  Advantageously, at least one of the contact surfaces of the knocker and the flange is equipped with a coating with a low coefficient of friction. It may especially be a Teflon type coating.
Un tel revêtement, bande téflon ou autre, permet d'obtenir un revêtement à faible coefficient de frottement qui ainsi peut servir de pièce d'usure.  Such a coating, Teflon tape or other, provides a low friction coating which can be used as a wear part.
Préférentiellement, la jonction de pan neaux acoustiq ues est équipée d'au moins un joint formant bavette aérodynamique. De manière préférentiellement, la jonction est équipée d'au moins un joint d'étanchéité. Avantageusement, le joint d'étanchéité est situé entre un panneau acoustique, et la bride. Preferably, the junction of acoustical panels is equipped with at least one aerodynamic flange seal. Preferably, the junction is equipped with at least one seal. Advantageously, the seal is located between an acoustic panel, and the flange.
La présente invention sera mieux comprise à la lumière de la description détaillée qui suit en regard du dessin annexé dans lequel :  The present invention will be better understood in the light of the following detailed description with reference to the appended drawing in which:
- la figure 1 est une représentation schématique partielle en coupe longitudinale d'une structure d'entrée d'air dite « laminaire » équipée d'un dispositif de centrage selon l'art antérieur,  FIG. 1 is a partial schematic representation in longitudinal section of a so-called "laminar" air intake structure equipped with a centering device according to the prior art,
- les figures 2 et 3 sont des représentations schématiques partielles en coupe long itud inale d 'u ne jonction entre un panneau interne et une portion de lèvre d'entrée d'air équipée d'un système de centrage selon l'invention,  FIGS. 2 and 3 are partial diagrammatic representations in longitudinal section of a junction between an inner panel and an air intake lip portion equipped with a centering system according to the invention,
- les figures 4a, 4b, 5a, 5b et 6a à 6d sont des représentations schématiques partielles des étapes de mise en place d'un joint formant bavette aérodynamique,  FIGS. 4a, 4b, 5a, 5b and 6a to 6d are partial schematic representations of the steps of setting up an aerodynamic flange seal,
- les figures 7 et 8 sont des représentations schématiques en coupe longitudinales d'une variante de réalisation de l'invention, FIGS. 7 and 8 are diagrammatic representations in longitudinal section of an alternative embodiment of the invention,
- l a fig u re 9 est une représentation schématique en coupe transversale correspondant à la structure d'entrée d'air des figures 7 et 8, FIG. 9 is a schematic cross-sectional representation corresponding to the air intake structure of FIGS. 7 and 8,
- les figures 10a à 10d sont des représentations schématiques partielles de la mise en place du joint formant bavette aérodynamique  FIGS. 10a to 10d are partial diagrammatic representations of the installation of the aerofoil flange gasket
La présente invention s'applique plus particulièrement aux nacelles dites « laminaires » présentant une structure d'entrée d'air 1 dont une paroi externe 2 est montée mobile en translation selon une direction longitudinale de la nacelle et intègre une portion de lèvre 2a d'entrée d'air.  The present invention more particularly applies to so-called "laminar" nacelles having an air inlet structure 1, an outer wall 2 of which is mounted to move in translation in a longitudinal direction of the nacelle and incorporates a lip portion 2a of air inlet.
Plus précisément, une telle structure d'entrée d'air pour nacelle de turboréacteur comprend au moins un panneau interne 3 destinée à être rattaché à un carter de soufflante (non visible) du turboréacteur et à constituer ainsi une partie fixe de ladite entrée d'air 1 , et au moins un panneau externe 2 mobile en translation selon une direction sensiblement longitudinale de la nacelle et intégrant une portion de lèvre 2a d'entrée d'air apte à assurer une jonction A0 entre le panneau interne fixe 3 et le panneau externe 2. Par ailleurs, ladite portion de lèvre 2a d'entrée d'air et ledit panneau interne 3 fixe sont chacun équipé au moins au niveau d'une extrémité de jonction, d'une structure d'atténuation acoustique se présentant sous la forme d'un panneau 5, 6 sandwiches à âme alvéolaire. More precisely, such an air intake structure for a turbojet engine nacelle comprises at least one inner panel 3 intended to be attached to a fan casing (not visible) of the turbojet engine and thus to constitute a fixed part of said air intake. air 1, and at least one outer panel 2 movable in translation in a substantially longitudinal direction of the nacelle and incorporating an air intake lip portion 2a adapted to provide a junction A0 between the fixed inner panel 3 and the outer panel 2. Moreover, said air inlet lip portion 2a and said fixed inner panel 3 are each equipped at least at a junction end with an acoustic attenuation structure in the form of a panel 5, 6 honeycomb sandwiches.
Conformément à l'art antérieur et tel que représenté sur la figure 1 , le centrage de la paroi externe 2 et de la lèvre d'entrée 2a d'air avec le panneau interne 3 est assuré au niveau d'une jonction A0 entre ladite portion de lèvre 2a d'entrée d'air et ladite paroi interne 3 au moyen de heurtoirs 7 fixés dans le panneau acoustique 5 côté lèvre 2a par l'intermédiaire d'une vis 7a avec un accès côté écrou à l'intérieur d'un C de fermeture 7b.  According to the prior art and as shown in Figure 1, the centering of the outer wall 2 and the air inlet lip 2a with the inner panel 3 is provided at a junction A0 between said portion of air inlet lip 2a and said inner wall 3 by means of knockers 7 fixed in the lip-side acoustic panel 2a by means of a screw 7a with a nut-side access inside a C closing 7b.
Une bavette aérodynamique 8 visant à optimiser l'écoulement du flux d'air au niveau de la jonction entre les panneaux est fixée selon le même principe.  An aerodynamic bib 8 to optimize the flow of air flow at the junction between the panels is set according to the same principle.
Une bride 9 fixée dans le panneau interne 3 vient, lors de la fermeture du panneau externe 2, en appui contre un joint 10 porté par une bride 1 1 correspondante de la portion de lèvre 2a d'entrée d'air afin d'assurer l'étanchéité de l'intérieur de la structure d'entrée d'air 1 . Cette bride permet également un appui pour les heurtoirs 7 et pour la bavette 8 aérodynamique.  A flange 9 fixed in the inner panel 3 comes, during the closing of the outer panel 2, against a seal 10 carried by a corresponding flange 1 1 of the lip portion 2a of air inlet to ensure the l sealing of the interior of the air intake structure 1. This flange also allows support for the knockers 7 and 8 aerodynamic bib.
Comme expliqué précédemment, ces fonctions impactent le début des zones acoustiques tant sur la portion de lèvre 2a d'entrée d'air que sur le panneau externe 3. Ainsi, les panneaux acoustiques 5, 6 doivent généralement être arrêtés avant la jonction A0 proprement dite entre ces deux structures. Il en résulte une perte de surface acoustique, et ce dans une zone où elle est particulièrement nécessaire.  As explained above, these functions impact the beginning of the acoustic zones on both the air intake lip portion 2a and on the outer panel 3. Thus, the acoustic panels 5, 6 must generally be stopped before the A0 junction itself. between these two structures. This results in a loss of acoustic surface, and this in an area where it is particularly necessary.
II existe ainsi un besoin pour une solution de centrage et fermeture permettant de conserver des panneaux acoustiques s'étendant au maximum jusqu'à la jonction A0 entre la portion de lèvre 2a d'entrée d'air et le panneau interne 3.  There is thus a need for a centering and closing solution that makes it possible to retain acoustic panels that extend as far as possible to the junction A 0 between the air intake lip portion 2 a and the inner panel 3.
A cette fin et comme représenté schématiquement sur les figures 2 et 3, le panneau acoustique 6 du panneau interne 3 présente une extrémité de jonction équipée d'un heurtoir 81 radial sur lequel est apte à venir reposer une bride 91 de jonction correspondante équipant une extrémité de jonction du panneau acoustique 5 de la portion de lèvre 2a d'entrée d'air lorsque celle-ci est en position de fermeture. Le heurtoir 81 porte une bande de revêtement 82 de type téflon à faible coefficient de frottement. Alternativement, la bande de revêtement 82 à faible coefficient de frottement pourra être portée par la bride 91 de jonction. For this purpose and as shown diagrammatically in FIGS. 2 and 3, the acoustic panel 6 of the inner panel 3 has a junction end equipped with a radial knocker 81 on which is able to rest a corresponding junction flange 91 fitted to one end joining the acoustic panel 5 of the air intake lip portion 2a when the latter is in the closed position. The knocker 81 carries a coating strip 82 of Teflon type with a low coefficient of friction. Alternatively, the coating strip 82 with a low coefficient of friction may be carried by the flange 91 junction.
Cette bande de revêtement possède une double fonction, à savoir de réduction des frottements lors de la fermeture de l'entrée d'air, et de pièce d'usure.  This coating strip has a dual function, namely reduction of friction during closing of the air inlet, and wear part.
La bande de revêtement peut-être disposée soit côté heurtoir 81 , soit fixée sous la bride 91 , ou être présente sur les deux éléments.  The coating strip may be disposed either on the knocker side 81, or fixed under the flange 91, or be present on both elements.
Afin d'assurer l'étanchéité de l'intérieur de la structure d'entrée d'air 1 , la bride de jonction 91 présente un retour 91 a d'extrémité portant un joint d'étanchéité 10 apte à coopérer avec une bride 92 d'étanchéité correspondante portée par le panneau interne (figure 2).  In order to ensure the tightness of the inside of the air intake structure 1, the connecting flange 91 has an end return 91a carrying a seal 10 adapted to cooperate with a flange 92d. corresponding seal carried by the inner panel (Figure 2).
Alternativement (figure 3), un joint d'étanchéité 101 peut être monté au niveau de l'extrémité de jonction du panneau interne 3 et venir en contact avec la bride de jonction 91 afin d'assurer l'étanchéité au plus près de ladite jonction A0. Le joint 101 pourra être intégré ou rapporté sur la bride de jonction 91 notamment pour ven ir en appu i contre le panneau interne 3 lors de la fermeture.  Alternatively (Figure 3), a seal 101 may be mounted at the junction end of the inner panel 3 and come into contact with the connecting flange 91 to ensure sealing closer to said junction A0. The seal 101 may be integrated or attached to the connecting flange 91 in particular to abut against the inner panel 3 during closing.
La bride de jonction 91 et la bride 92 du panneau interne 3 peuvent être alors utilisées pour la mise en place de butées axiales 20 et/ou de verrous entre la portion de lèvre 2a/panneau externe 2 et le panneau interne 3.  The junction flange 91 and the flange 92 of the inner panel 3 can then be used for the introduction of axial stops 20 and / or locks between the lip portion 2a / outer panel 2 and the inner panel 3.
De préférence, le joint d'étanchéité 1 0, 1 01 équipera toute la circonférence de la structure.  Preferably, the seal 1 0, 1 01 will equip the entire circumference of the structure.
Les heurtoirs 81 seront également avantageusement disposés le long de la circonférence de la structure 1 et préférentiellement répartis de manière discrète, avantageusement uniformément. Bien évidemment, il pourra également s'agir d'un heurtoir 81 continu décrivant sensiblement toute la circonférence.  The knockers 81 will also advantageously be arranged along the circumference of the structure 1 and preferentially distributed discretely, advantageously uniformly. Of course, it may also be a continuous knocker 81 describing substantially the entire circumference.
Comme on le constate sur les figures, grâce à l'invention les débuts des surfaces acoustiques de la portion de lèvre 2a d'entrée d'air et du panneau interne 3 sont au plus près de la jonction A0 entre ces deux panneaux, ce qui améliore le traitement acoustique de l'ensemble de la structure d'entrée d'air 1 .  As can be seen from the figures, thanks to the invention the beginnings of the acoustic surfaces of the air intake lip portion 2a and of the inner panel 3 are as close as possible to the A0 junction between these two panels, which improves the acoustic treatment of the entire air intake structure 1.
Bien évidemment, la disposition inverse (heurtoir 81 sur la portion de lèvre 2a, et bride de jonction 91 sur le panneau interne 3) est également possible. La jonction AO entre la portion de lèvre 2a d'entrée d'air et le panneau interne 3 peut-être par ailleurs équipée d'un joint formant bavette aérodynamique 102. Of course, the reverse arrangement (knocker 81 on the lip portion 2a, and junction flange 91 on the inner panel 3) is also possible. The junction AO between the air intake lip portion 2a and the inner panel 3 may also be equipped with an aerodynamic flange seal 102.
Sa mise en place est détaillée sur les figures 4a, 4b, 5a, 5b et 6a à 6d.  Its implementation is detailed in Figures 4a, 4b, 5a, 5b and 6a to 6d.
La bavette aérodynam ique 102 présente une structure souple élastique montée sur une peau supérieure d'un panneau acoustique 5 de la portion de lèvre 2a d'entrée d'air.  The aerodynamic flap 102 has a flexible elastic structure mounted on an upper skin of an acoustic panel 5 of the lip portion 2a of air inlet.
La bavette 102 s'étend le long de l'épaisseur dudit panneau acoustique 5 au niveau de son extrémité de jonction A0 et présente un retour inférieur 102a s'étendant de part et d'autre de ladite jonction A0, tant sur la portion de lèvre 2a d'entrée d'air que sur le panneau interne (non représenté sur les figures 4a, 4b, 5a, 5b), assurant ainsi un recouvrement aérodynamique de la jonction.  The flap 102 extends along the thickness of said acoustic panel 5 at its junction end A0 and has a lower return 102a extending on either side of said junction A0, both on the lip portion. 2a of air intake only on the inner panel (not shown in Figures 4a, 4b, 5a, 5b), thus providing an aerodynamic recovery of the junction.
Les figures 4a et 5a sont des vues de face en coupe transversale dudit joint 102 formant bavette aérodynamique.  Figures 4a and 5a are cross-sectional front views of said aerodynamic bib seal 102.
La mise en place du joint 102 autour de l'épaisseur du panneau acoustique de la portion de lèvre d'entrée d'air s'effectuera par l'intermédiaire d'une cale 103 de montage.  The establishment of the seal 102 around the thickness of the acoustic panel of the air intake lip portion will be effected via a shim 103 mounting.
Comme visible sur les figures 6a à 6d, une partie inférieure de la bavette (côté veine) s'écarte du panneau acoustique et permet le montage du panneau acoustique appartenant au panneau interne.  As shown in Figures 6a to 6d, a lower part of the flap (vein side) deviates from the acoustic panel and allows the mounting of the acoustic panel belonging to the inner panel.
Les figures 7 à 9 et 10a à 1 0d sont des vues d'un deuxième mode de réalisation d'une structure d'entrée d'air 1 10 selon l'invention dans lequel les heurtoirs 81 appartiennent au panneau acoustique 5 de la portion de lèvre 2a et la bride de jonction 91 appartient au panneau acoustique 6 du panneau interne 3.  Figures 7 to 9 and 10a to 10d are views of a second embodiment of an air intake structure 1 10 according to the invention in which the knockers 81 belong to the acoustic panel 5 of the portion of lip 2a and the connecting flange 91 belongs to the acoustic panel 6 of the inner panel 3.
Plus précisément, la figure 7 est en vue en coupe longitudinale prise sensiblement au niveau de moyens de verrouillage 21 (ou butées axiales 20). Le figure 8 est une vue en coupe longitudinale prise en section courante.  More specifically, Figure 7 is in longitudinal sectional view taken substantially at locking means 21 (or axial stops 20). Figure 8 is a longitudinal sectional view taken in current section.
La figure 9 est une vue en coupe transversale de face en section courante.  Figure 9 is a cross sectional view of the face in current section.
Les figures 10a à 10d sont sensiblement équivalentes aux figures 6a à 6d et illustrent la mise en place du joint 102 formant bavette aérodynamique. On notera également que dans ce mode de réalisation, le joint 102 réalise également la fonction du joint d'étanchéité 10 et 101 au moyen d'une languette supérieure 104 qui vient en contact contre la bride de jonction 91 lors de la fermeture de la structure (direction de fermeture représentée par la flèche sur la figure 10c). Figures 10a to 10d are substantially equivalent to Figures 6a to 6d and illustrate the establishment of the seal 102 aerodynamic flap. Note also that in this embodiment, the seal 102 also performs the function of the seal 10 and 101 by means of an upper tab 104 which comes into contact against the connecting flange 91 when closing the structure (closing direction represented by the arrow in Figure 10c).
Bien que l'invention ait été décrite avec un exemple particulier de réal isation, il est bien évident qu'elle n'y est nullement limitée et qu'elle comprend tous les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention.  Although the invention has been described with a particular example of real isation, it is obvious that it is in no way limited and that it includes all the technical equivalents of the means described and their combinations if they enter in the context of the invention.
II convient notamment de noter que l'entrée d'air translatable forme de manière générale un manchon amovible ajustable sur un conduit que forme la structure de base de la nacelle. Ainsi, le système de centrage et d'étanchéité objet de la présente invention peut s'appliquer de manière générale à tout type de manchon amovible que l'on souhaiterait positionner de manière centrée et étanche sur une extrémité d'un conduit.  In particular, it should be noted that the translatable air inlet generally forms an adjustable removable sleeve on a conduit formed by the base structure of the nacelle. Thus, the centering and sealing system object of the present invention can be applied generally to any type of removable sleeve that would be desired to centrally position and sealed on one end of a conduit.

Claims

REVENDICATIONS
1 . Structure d'entrée d'air (1 10) pour nacelle de turboréacteur comprenant au moins un panneau interne (3) destinée à être rattaché à un carter de soufflante du turboréacteur et à constituer ainsi une partie fixe de ladite entrée d'air, et au moins un panneau externe (2) mobile en translation selon une direction sensiblement longitudinale de la nacelle et intégrant une portion de lèvre (2a) d'entrée d'air apte à assurer une jonction entre le panneau interne fixe et le panneau externe, ladite portion de lèvre d'entrée d'air et ledit panneau interne fixe étant chacun équipés au moins au niveau d'une extrémité de jonction, d'une structure d'atténuation acoustique (5, 6), caractérisé en ce qu'au moins l'une des extrémités de jonction est équipée d'au moins un heurtoir (81 ) radial apte à venir en contact avec une bride (91 ) de jonction correspondante présentée par l'autre extrémité de jonction lorsque le panneau externe mobile est en position de fermeture. 1. An air intake structure (1 10) for a turbojet engine nacelle comprising at least one inner panel (3) intended to be attached to a turbojet engine fan casing and to thus constitute a fixed part of said air intake, and at least one outer panel (2) movable in translation in a substantially longitudinal direction of the nacelle and integrating an air intake lip portion (2a) adapted to ensure a junction between the fixed inner panel and the outer panel, said air intake lip portion and said fixed inner panel being each equipped at least at a junction end with an acoustic attenuation structure (5, 6), characterized in that at least one one of the junction ends is provided with at least one radial knocker (81) adapted to come into contact with a corresponding junction flange (91) presented by the other junction end when the movable outer panel is in the closed position .
2. Structure (1 10) selon la revendication 1 , caractérisée en ce que le heurtoir (81 ) est intégré au panneau acoustique (5, 6) de son extrémité de jonction. 2. Structure (1 10) according to claim 1, characterized in that the knocker (81) is integrated with the acoustic panel (5, 6) of its junction end.
3. Structure (1 10) selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que la bride (91 ) correspondante est intégrée au panneau acoustique (5, 6) de son extrémité de jonction. 3. Structure (1 10) according to any one of claims 1 or 2, characterized in that the flange (91) is integrated with the acoustic panel (5, 6) of its junction end.
4. Structure (1 10) selon l'une quelconque des revendications 1 à 3, caractérisée en ce qu'elle comprend plusieurs heurtoirs (81 ) répartis sur une circonférence de l'extrémité de jonction. 4. Structure (1 10) according to any one of claims 1 to 3, characterized in that it comprises several knockers (81) distributed on a circumference of the junction end.
5. Structure (1 10) selon l'une quelconque des revendications 1 à 4, caractérisée en ce qu'au moins une des surfaces de contact du heurtoir (81 ) et de la bride (91 ) est équipée d'un revêtement (82) à faible coefficient de frottement pouvant servir de pièce d'usure. 5. Structure (1 10) according to any one of claims 1 to 4, characterized in that at least one of the contact surfaces of the knocker (81) and the flange (91) is equipped with a coating (82). ) with a low coefficient of friction that can serve as a wear part.
6. Structure (1 10) selon l'une quelconque des revendications 1 à 5, caractérisée en ce que la jonction (A0) de panneaux acoustiques est équipée d'au moins un joint (102) formant bavette aérodynamique. 6. Structure (1 10) according to any one of claims 1 to 5, characterized in that the junction (A0) of acoustic panels is equipped with at least one seal (102) aerodynamic flap.
7. Structure (1 10) selon l'une quelconque des revendications 1 à 6, caractérisée en ce que la jonction (AO) est équ ipée d'au moins un joint d'étanchéité (10). 7. Structure (1 10) according to any one of claims 1 to 6, characterized in that the junction (AO) is equ ipated with at least one seal (10).
8. Structure (1 10) selon l'une quelconque des revendications 1 à 7, caractérisée en ce que le joint d'étanchéité (10) est situé entre un panneau acoustique, et la bride. 8. Structure (1 10) according to any one of claims 1 to 7, characterized in that the seal (10) is located between an acoustic panel, and the flange.
EP13715366.4A 2012-03-29 2013-03-21 Turbojet engine nacelle air intake structure of laminar type Withdrawn EP2831393A1 (en)

Applications Claiming Priority (2)

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FR1252815A FR2988778B1 (en) 2012-03-29 2012-03-29 AIR INTAKE STRUCTURE OF LAMINAR TYPE TURBOREACTOR NACELLE AIRCRAFT
PCT/FR2013/050610 WO2013144485A1 (en) 2012-03-29 2013-03-21 Turbojet engine nacelle air intake structure of laminar type

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EP (1) EP2831393A1 (en)
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BR (1) BR112014024025A8 (en)
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BR112014024025A2 (en) 2017-06-20
RU2014142817A (en) 2016-05-20
CN104220728A (en) 2014-12-17
US20150007896A1 (en) 2015-01-08
BR112014024025A8 (en) 2017-07-25
FR2988778B1 (en) 2014-03-21
US9938897B2 (en) 2018-04-10
CA2868146A1 (en) 2013-10-03
FR2988778A1 (en) 2013-10-04
WO2013144485A1 (en) 2013-10-03

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